CN210761279U - Emergent braking system of aircraft - Google Patents
Emergent braking system of aircraft Download PDFInfo
- Publication number
- CN210761279U CN210761279U CN201921544271.8U CN201921544271U CN210761279U CN 210761279 U CN210761279 U CN 210761279U CN 201921544271 U CN201921544271 U CN 201921544271U CN 210761279 U CN210761279 U CN 210761279U
- Authority
- CN
- China
- Prior art keywords
- hydraulic
- brake
- pressure
- oil
- electromagnetic valve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
- 239000007788 liquid Substances 0.000 abstract 1
- 238000006243 chemical reaction Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 6
- 230000007547 defect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 230000003137 locomotive effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
Images
Landscapes
- Regulating Braking Force (AREA)
Abstract
A brake oil port of a hydraulic electromagnetic valve is communicated with an oil inlet of a hydraulic cylinder seat of an airplane wheel. An oil inlet of the hydraulic pressure reducing brake valve is externally connected with a hydraulic source. One binding post of the single-pole double-position switch of the hydraulic relay is connected with a direct-current power supply, and the other binding post is connected with an electromagnet of the hydraulic electromagnetic valve through a lead. When the pressure of oil liquid from the hydraulic pressure reducing brake valve reaches the contact connection pressure of the hydraulic relay, the contact of the hydraulic relay is conducted, and the direct-current power supply is conducted with the electromagnet on the hydraulic electromagnetic valve, so that the hydraulic electromagnetic valve is relieved, and the pressure of the emergency brake system with the active anti-skidding brake function is reduced. The utility model discloses emergent braking system with initiative anti-skidding brake function can compare actual brake pressure and the brake pressure value of system setting to initiative adjustment brake pressure reaches the mesh that can take the initiative antiskid.
Description
Technical Field
The invention relates to the field of airplane brake systems, in particular to an emergency brake system with an active anti-skidding brake function.
Background
In order to make the airplane land safely and ensure the ground control safety of the airplane, according to the requirements and regulations of an emergency brake system in the antiskid brake control system general specification (GJB2879A-2008) of the airplane wheel: "in case of failure or malfunction of the normal braking system, the emergency braking system must safely brake the airplane, and the emergency braking system and the normal braking system must be independent from each other".
The emergency brake system of the airplane mostly adopts a manual operation mode to brake and consists of a single hydraulic pressure reducing brake valve or a single air pressure reducing brake valve. The emergency brake system has no antiskid function, and the output emergency brake pressure is in direct proportion to the operating force.
The on-off antiskid control principle is adopted in the Su 27 aircraft brake system, and the accessories of the normal brake system comprise a pressure relief valve, a modulator, an electromagnetic valve and an antiskid automaton; the antiskid control accessories comprise a hydraulic switch, a speed sensor, an electromagnetic valve and an antiskid automat. The brake oil port of the pressure-reducing valve is communicated with the oil inlet of the hydraulic switch, the oil outlet of the hydraulic switch is communicated with the oil inlet of the modulator, the oil outlet of the modulator is communicated with the oil inlet of the electromagnetic valve, and the brake oil port of the electromagnetic valve is communicated with the oil inlet of the anti-skid automatic device; the brake oil port of the antiskid automatic device is communicated with a brake device; one terminal of the hydraulic switch is communicated with a power supply, the other terminal of the hydraulic switch is communicated with one end of the front wheel speed sensor, and the other end of the front wheel speed sensor is communicated with the electromagnet of the electromagnetic valve through a lead; an oil return port of the pressure reducing valve is communicated with the oil tank through an oil return pipe; an oil return port of the electromagnetic valve is communicated with the oil tank through a pipeline; the oil inlet of the pressure reducing valve is externally connected with a hydraulic source through a pipeline. In the braking process, if a certain wheel is stuck or the wheel is decelerated too violently, the anti-skid control system works and consists of an electric part and a mechanical part, after the airplane lands, a front wheel speed sensor switch is switched on, and a wheel speed sensor is switched off, when the rotating speed of the wheel is reduced to a value corresponding to the linear speed, the speed sensor switch on the wheel is switched on, so that an electromagnetic valve works, the oil coming from the brake is cut off, a brake device is communicated with an oil return circuit, and the brake is released. The wheel speed sensor is normally closed, the front wheel speed sensor is normally open, the circuit of an antiskid system is disconnected when the speed of the airplane is low, and antiskid control is completely borne by a mechanical part. The antiskid automaton is a main accessory for mechanical antiskid. When the angular speed deceleration of the airplane wheel reaches a given value, the oil return valve of the anti-skid automatic device is opened, so that the airplane wheel is released to brake. And braking after the tire dragging is released.
The braking system of Su 27 airplane is composed of simple hydraulic and electric accessories, and has complex structure and poor antiskid function, but adopts a double-signal working mode and applies a tyre dragging automatic machine and a hydraulic amplitude limiter, so that the antiskid function is improved, and the braking system has the characteristics of safe system, stable braking and high braking efficiency. However, the su27 aircraft brake system is not an emergency brake system, but a normal anti-skid brake system using an on-off anti-skid control principle.
The invention with application number 201610902426.5 creates an airplane electronic anti-skid braking system for ensuring emergency braking operation, which comprises a normal braking system and an emergency braking system. The normal braking system mainly comprises a brake valve, an electro-hydraulic servo valve, a control box and an airplane wheel speed sensor; the emergency brake system mainly comprises an emergency brake valve, a conversion valve and a switch, and the normal brake system and the emergency brake system are connected and converted through the conversion valve. The normal braking system and the emergency braking system adopt two sets of independent pressure supply source systems. The invention improves the system structure by adding the control device, so that normal braking can be disabled during emergency braking, the switching valve can be completely switched under the action of the emergency braking pressure, and even if the emergency braking and the normal braking are used simultaneously, the switching valve can be switched to an emergency braking system. Thereby ensuring the implementation of emergency braking and fundamentally eliminating the failure of the emergency braking and the accident hidden danger caused by the simultaneous use of the emergency braking and the normal braking. However, the emergency brake system provided by the invention has no antiskid function.
The invention with application number 201610902427.X provides an airplane brake system for preventing improper use of emergency brake, which comprises a normal brake system and an emergency brake system. The normal braking system comprises a braking instruction sensor, an electromagnetic hydraulic lock, an electro-hydraulic servo valve, a control box and an airplane wheel speed sensor. The emergency brake system comprises an emergency brake valve, a conversion valve and a switch. The normal braking system and the emergency braking system are connected and converted through the conversion valve. If normal braking is used during emergency braking, the invention forces the normal braking system to release pressure, so that the normal input port of the conversion valve has no pressure, and the conversion valve is completely converted into the emergency braking system, thereby ensuring the implementation of emergency braking, and fundamentally eliminating the failure of the emergency braking and the accident potential caused by the simultaneous use of the emergency braking and the normal braking. However, the emergency brake system provided by the invention has no antiskid function.
The invention creation 'an aircraft inertia antiskid braking system for ensuring emergency braking' of application number 201610906014.9, the invention creation by normal braking system and emergency braking system, normal braking system and emergency braking system adopt two sets of independent pressure supply source system, and through the conversion valve conversion. The invention improves the system structure by adding the control device, so that normal braking can be disabled during emergency braking, and the switching valve can be completely switched under the action of the emergency braking pressure. However, the emergency brake system provided by the invention has no antiskid function.
The invention with the application number of 201811188978.X creates 'a remote control emergency brake system and a design method thereof', and the invention creates the method that a brake command sensor arranged in a cockpit directly controls an electromagnetic hydraulic lock and an electro-hydraulic pressure servo valve arranged in a main landing gear cabin, thereby realizing the remote control of the emergency brake system. The electromagnetic hydraulic lock and the electro-hydraulic pressure servo valve which are installed in the main landing gear cabin are connected to a hydraulic source nearby, and the hydraulic pipeline of the braking system is arranged in the main landing gear cabin close to the brake wheels, so that the problem that the hydraulic pipeline needs to enter the cockpit is solved, the length of the hydraulic pipeline is reduced, the emergency braking system is simple to maintain, and the complexity and the maintenance difficulty of the emergency braking system are reduced. However, the emergency brake system provided by the invention has no antiskid function.
Through retrieval, the emergency brake system in the prior art has no anti-skid function, and a specific schematic diagram of the emergency brake system without the anti-skid function is shown in an emergency brake system of a certain machine in fig. 1. The brake pressure is lower than that of a normal brake system, the emergency brake system has no antiskid function, and the emergency brake system has no relevant data on the aspect of active antiskid brake control. The emergency brake system controls an emergency brake handle by a pilot to enable an emergency brake valve to output brake pressure to realize emergency brake control for braking and stopping an airplane, but the emergency brake system without an active anti-skid function has no anti-skid function, and if the bonding torque of the ground is sharply reduced under special conditions such as rain, ice, snow, oil tracks and the like, the emergency brake system can not release pressure through active anti-skid, and accidents of tire dragging by a locomotive or tire burst can be caused as long as the brake torque is larger than the bonding torque of the ground.
Disclosure of Invention
The invention provides an emergency brake system for an airplane, aiming at overcoming the defect that when the brake torque of the emergency brake system without an active anti-skidding function is larger than the ground combination torque, the accident that the tire is dragged by the airplane wheel or is blown out is caused in the prior art.
The emergency brake system of the airplane comprises a hydraulic electromagnetic valve, a hydraulic relay, a hydraulic pressure-reducing brake valve and a 28V direct-current power supply; wherein: a brake oil port of the hydraulic pressure-reducing brake valve is respectively communicated with an oil inlet of the hydraulic relay and an oil inlet of the hydraulic electromagnetic valve through a pressure oil pipe; and an oil return port of the hydraulic pressure-reducing brake valve is communicated with an oil tank through an oil return pipe. And a brake oil port of the hydraulic electromagnetic valve is communicated with an oil inlet of a hydraulic cylinder seat of the airplane wheel. An oil return tank of the hydraulic electromagnetic valve is communicated with the oil tank through a pipeline. And an oil inlet of the hydraulic pressure-reducing brake valve is connected with a hydraulic source through a pipeline. One binding post of a single-pole double-position switch in the hydraulic relay is connected with a 28V direct-current power supply, and the other binding post of the single-pole double-position switch of the hydraulic relay is connected with an electromagnet in the hydraulic electromagnetic valve through a lead. And oil return ports of the hydraulic pressure-reducing brake valve, the hydraulic relay and the hydraulic electromagnetic valve are communicated with an oil tank through oil return pipes.
The 28V direct-current power supply is communicated with a normally open contact of the positive electrode of the hydraulic relay; the contact of the negative pole of the hydraulic relay is connected with the positive pole of the hydraulic electromagnetic valve; the negative pole of the hydraulic electromagnetic valve is connected to the ground wire of the airplane power supply system. When the oil pressure is equal to or greater than the contact-making pressure of the hydraulic relay, the contact of the hydraulic relay is made, the 28V direct-current power supply is connected with the hydraulic electromagnetic valve, and the pressure of the emergency brake system is reduced.
The emergency brake system with the active anti-skidding function is composed of a hydraulic pressure reducing brake valve, a hydraulic relay and a hydraulic electromagnetic valve. The working principle of the emergency brake system with the active anti-skid brake function is as follows:
1) and an emergency brake switch is switched on, a pilot presses an emergency brake handle, the hydraulic pressure reducing brake valve 4 outputs brake pressure smaller than intermediate brake pressure, and an emergency brake system with an active anti-skidding function does not work.
2) The brake pressure output by the hydraulic pressure reducing brake valve 4 is greater than the intermediate brake pressure P of the emergency brake systems1When the emergency brake system with the active anti-skidding function works; the brake pressure output by the hydraulic pressure reducing brake valve 4 is greater than the maximum brake pressure P of the emergency brake systemsWhen the pressure is higher than the contact connection pressure of the hydraulic relay, the contact of the hydraulic relay 3 is connected, and meanwhile, the hydraulic electromagnetic valve 2 is electrified, so that the emergency brake pressure is reduced; when the brake pressure of the hydraulic pipeline is lower than the contact disconnection pressure of the hydraulic relay 3, the contact of the hydraulic relay 3 is disconnected, the hydraulic electromagnetic valve 2 is powered off, and the emergency brake pressure rises. The pilot presses the emergency brake handle to the end, and the emergency brake system carries out brake control according to the preset control rate until the airplane is braked and stopped.
The brake pressure curve of the emergency brake system with the active anti-skid brake function in working is shown in figure 3.
The invention provides an aircraft emergency brake system and a design method thereof, aiming at overcoming the defect that the emergency brake system without an active anti-skid function can cause tire dragging or tire burst accidents when the brake torque is larger than the ground binding torque in the prior art, and aiming at researching the in-plant test curve of a normal brake system and referring to the standards of the outfield test flight, the test and the use conclusion of the normal brake system. The emergency brake switch is switched off, the emergency brake system with the active anti-skid brake function does not work, a pilot presses the emergency brake handle, and the hydraulic pressure reducing brake valve outputs brake pressure. The force sense difference of the pilot is obvious in the operation process, and safe and reliable braking can be realized by means of the pilot operation. Because the pilot has the difference of strength in the operation process, the emergency brake system with the active anti-skidding brake function is convenient to use and has a good human-computer interface. When the operating force is small, the output brake pressure is lower than the middle brake pressure, and safe and reliable braking can be realized; when the operating force is increased, the force sense is obvious, and the output brake pressure is higher than the intermediate brake pressure, the emergency brake system with the active anti-skid brake function can compare the actual brake pressure with the brake pressure value set by the system, so that the brake pressure is actively adjusted, and the purpose of active anti-skid is achieved. And realizing safe braking.
The invention adds an active anti-skid braking function in an emergency braking system. The invention is used for solving the defect that when the braking torque of a braking system is larger than the ground combined torque, the tire dragging or tire burst of the airplane wheel can be caused. The working strength of pilots is reduced, and the landing safety of the airplane is ensured.
The invention has two points:
1. an active anti-skid brake control function is added in the emergency brake system; the emergency braking system is used for solving the defect that when the braking torque of the braking system is larger than the ground combined torque, the tire dragging of the aircraft wheels or the tire burst accident can be caused, the working strength of a pilot is reduced, the landing safety of the aircraft is ensured, and the tire burst accident can be prevented without adopting the snub operation when the pilot uses the emergency brake.
2. And (5) performing PWM control on the brake pressure of the emergency brake system. According to the invention, the pressure relay is selected, the emergency brake system selects the test and test flight experience of the normal brake system, and the brake pressure PWM control of the emergency brake system is realized by controlling the flow and the pressure of the hydraulic pressure reduction brake valve. In conclusion, the invention aims to solve the practical problems of increasing the anti-skidding function in the emergency brake system, reducing the workload of pilots and avoiding the tire burst accident when the brake system is used. "
Drawings
FIG. 1 is a schematic structural diagram of an emergency braking system of a certain machine;
FIG. 2 is a schematic structural view of the present invention;
fig. 3 is an operating curve of the present invention.
1. A machine wheel; 2. a hydraulic solenoid valve; 3. a hydraulic relay; 4. a hydraulic pressure reducing brake valve; 5. a pressure oil pipe; 6. an oil return pipe; 7. an oil tank; 8.28V DC power supply.
Detailed Description
The embodiment is an emergency brake system with an active anti-skid brake function, and the emergency brake system comprises a hydraulic electromagnetic valve 2, a hydraulic relay 3, a hydraulic pressure-reducing brake valve 4, a 28V direct-current power supply 8 and an oil return pipe 6. Wherein: a brake oil port of the hydraulic pressure-reducing brake valve 4 is respectively communicated with an oil inlet of the hydraulic relay 3 and an oil inlet of the hydraulic electromagnetic valve 2 through a pressure oil pipe 5; the oil return port of the hydraulic pressure-reducing brake valve 4 is communicated with an oil tank 7 through an oil return pipe 6. And a brake oil port of the hydraulic electromagnetic valve 2 is communicated with an oil inlet of a hydraulic cylinder seat of the airplane wheel. An oil return tank of the hydraulic electromagnetic valve 2 is communicated with an oil tank 7 through a pipeline. And an oil inlet of the hydraulic pressure-reducing brake valve 4 is connected with a hydraulic source through a pipeline.
One terminal of a single-pole double-position switch in the hydraulic relay 3 is connected with the 28V direct-current power supply 8, and the other terminal of the single-pole double-position switch of the hydraulic relay 3 is connected with an electromagnet in the hydraulic electromagnetic valve 2 through a lead. When the emergency brake system works, when the brake pressure output by the hydraulic pressure reduction brake valve 4 reaches the contact connection pressure of the hydraulic relay 3, the hydraulic relay is connected, the 28V direct-current power supply is connected with the electromagnet on the hydraulic electromagnetic valve 2, so that the hydraulic electromagnetic valve 2 discharges oil and releases pressure, and the pressure of the emergency brake system with the active anti-skidding brake function is reduced.
In the embodiment, a hydraulic source is connected to an oil inlet of a hydraulic pressure reducing brake valve 4 through a pipe joint of M12 and an oil pipe 5 with the length of 3.6M and the inner diameter of 5.5 mm; a brake oil port of the hydraulic pressure-reducing brake valve 4 is connected with the hydraulic relay 3 through a three-way pipe, a pipe joint of M12 and an oil pipe 5 with the length of 0.2M, and the other connector of the three-way pipe joint is communicated with an oil inlet of the hydraulic electromagnetic valve 2 through the pipe joint of M12 and the oil pipe 5 with the length of 2.1M and the inner diameter of phi 5.5 mm; oil enters the hydraulic cylinder seat of the wheel 1 from the brake working port of the hydraulic electromagnetic valve 2 through a pipe joint of M12 and an oil pipe with the length of 1.5M and the inner diameter of phi 5.5mm to push the hydraulic cylinder to work so as to brake.
The oil return pipe 6 connects return oil of the hydraulic pressure-reducing brake valve 4, the hydraulic relay 3 and the hydraulic solenoid valve 2 and connects the return oil to the oil tank 7, and the return oil is led to the oil tank 7 when the system brake pressure is reduced.
The 28V direct-current power supply 8 of the airplane power supply system is communicated with a normally open contact of the positive pole of the hydraulic relay 3; the contact of the negative pole of the hydraulic relay 3 is connected with the positive pole of the hydraulic electromagnetic valve 2; the negative pole of the hydraulic electromagnetic valve 2 is connected to the ground wire of the airplane power supply system. When the oil pressure is equal to or greater than the contact-making pressure of the hydraulic relay 3, the contact of the hydraulic relay 3 is made, the 28V direct-current power supply is connected with the hydraulic electromagnetic valve 2, and the pressure of the emergency brake system is reduced.
Claims (2)
1. An emergency brake system of an airplane is characterized by comprising a hydraulic electromagnetic valve, a hydraulic relay, a hydraulic pressure-reducing brake valve and a 28V direct-current power supply; wherein: a brake oil port of the hydraulic pressure-reducing brake valve is respectively communicated with an oil inlet of the hydraulic relay and an oil inlet of the hydraulic electromagnetic valve through a pressure oil pipe; an oil return port of the hydraulic pressure-reducing brake valve is communicated with an oil tank through an oil return pipe; a brake oil port of the hydraulic electromagnetic valve is communicated with an oil inlet of a hydraulic cylinder seat of the airplane wheel; an oil return tank of the hydraulic electromagnetic valve is communicated with an oil tank through a pipeline; an oil inlet of the hydraulic pressure-reducing brake valve is connected with a hydraulic source through a pipeline; one binding post of a single-pole double-position switch in the hydraulic relay is connected with a 28V direct-current power supply, and the other binding post of the single-pole double-position switch of the hydraulic relay is connected with an electromagnet in a hydraulic electromagnetic valve through a lead; and oil return ports of the hydraulic pressure-reducing brake valve, the hydraulic relay and the hydraulic electromagnetic valve are communicated with an oil tank through oil return pipes.
2. An aircraft emergency brake system according to claim 1, wherein the 28V dc power supply is in communication with a normally open contact on the positive pole of the hydraulic relay; the contact of the negative pole of the hydraulic relay is connected with the positive pole of the hydraulic electromagnetic valve; the negative electrode of the hydraulic electromagnetic valve is connected to the ground wire of the airplane power supply system; when the oil pressure is equal to or greater than the contact-making pressure of the hydraulic relay, the contact of the hydraulic relay is made, the 28V direct-current power supply is connected with the hydraulic electromagnetic valve, and the pressure of the emergency brake system is reduced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921544271.8U CN210761279U (en) | 2019-09-17 | 2019-09-17 | Emergent braking system of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921544271.8U CN210761279U (en) | 2019-09-17 | 2019-09-17 | Emergent braking system of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210761279U true CN210761279U (en) | 2020-06-16 |
Family
ID=71065901
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921544271.8U Withdrawn - After Issue CN210761279U (en) | 2019-09-17 | 2019-09-17 | Emergent braking system of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210761279U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110606195A (en) * | 2019-09-17 | 2019-12-24 | 西安航空制动科技有限公司 | Airplane emergency brake system and design method thereof |
| CN112209275A (en) * | 2020-11-16 | 2021-01-12 | 中船华南船舶机械有限公司 | Brake valve |
-
2019
- 2019-09-17 CN CN201921544271.8U patent/CN210761279U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110606195A (en) * | 2019-09-17 | 2019-12-24 | 西安航空制动科技有限公司 | Airplane emergency brake system and design method thereof |
| CN110606195B (en) * | 2019-09-17 | 2024-05-24 | 西安航空制动科技有限公司 | Airplane emergency braking system and design method thereof |
| CN112209275A (en) * | 2020-11-16 | 2021-01-12 | 中船华南船舶机械有限公司 | Brake valve |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3636504B1 (en) | A system for controlling backup air brake for a locomotive | |
| CN103158867B (en) | Airplane electrical signal transmission brake antiskid control system | |
| CN210761279U (en) | Emergent braking system of aircraft | |
| CN103158868B (en) | Mixed airplane brake system and control method | |
| CN106394880B (en) | A kind of aircraft electronic anti-skid brake system (ABS) ensuring emergency brake operation | |
| CN204527622U (en) | A kind of unmanned plane brake system | |
| WO2021097970A1 (en) | Emergency brake control device, emergency brake system, and rail vehicle | |
| CN111942423B (en) | Parking brake control system, control method and vehicle | |
| CN106428533B (en) | A kind of airplane inertial anti-skid brake system (ABS) ensuring emergency brake | |
| CN106477066A (en) | A kind of aircraft bowser being equipped with automatic transmission | |
| CN212796891U (en) | Emergency braking control system of straight-through brake for urban rail vehicle | |
| CN106394525A (en) | Airplane telex brake system directly controlled by brake instruction | |
| CN110606195B (en) | Airplane emergency braking system and design method thereof | |
| CN203819258U (en) | Automatic control system for car coupler | |
| CN108099874B (en) | Airplane automatic braking system directly controlled by automatic brake switch | |
| CN109515698A (en) | A kind of various dimensions constant speed antiskid control system | |
| CN110525406B (en) | Electromagnetic air braking system of low-speed traction locomotive and implementation method thereof | |
| CN106364668A (en) | Airplane brake-by-wire braking system for preventing emergency brake from being improperly used | |
| CN103496361A (en) | Unmanned control braking device, method and vehicle | |
| CN108082154B (en) | Aircraft hydraulic braking system with automatic braking capability | |
| CN203753122U (en) | Automatic hydraulic brake system for realizing intelligent driving | |
| CN111775999B (en) | Train pipe quantitative pressure reduction control system and method | |
| CN108100241B (en) | Airplane fly-by-wire brake system capable of automatically braking and brake method | |
| RU2726298C1 (en) | Emergency stop braking system of aircraft and towing carrier | |
| CN108146622B (en) | Airplane fly-by-wire brake system using automatic brake switch and brake method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20200616 Effective date of abandoning: 20240524 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20200616 Effective date of abandoning: 20240524 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |